Test simulation study on flutter characteristics of airfoil

Abstract

Abstract: Aircraft stalling, air parking and airfoil flutter are three important factors that affect aircraft flight safety. It is always a critical issue in the field of flight data to fully carry out the flutter airworthiness measurement. To reduce the workload of flutter airworthiness measurement and to make the vibration test point selection more targeted, an analysing method aiming at the flutter characteristics of airfoils are proposed basing on fluid solid coupling,taking B737-800 as study object. Firstly, using coupled flow field to compute the wing mode, then by mapping coupled modes to the harmonic response and transient dynamics analysis of the wing, it would access to the regularity of flutter characteristics of the wing, thus the flutter danger points would be found out. Analysis of simulation results show that the wing deformation is mainly located in the 22%~60% wingspan area and 85% wingspan to wingtip, which is consistent with the selection of flutter measurement position in the research center of Langley. The changing trend of wing twist along semispan in flutter test simulation is matched with test results of Langley, thus it would provide reference for the analysis of wing flutter failure as well as the selection of excitation test points for the measurement of flutter airworthiness.

Key words: flutter airworthiness, coupled flow field, coupled mode, harmonic response analysis, transient dynamic analysis

CLC Number:

YU Zhijing, HUA Zhen, WANG Shuo, WANG Wei, WU Jun, ZHUGE Jingchang. Test simulation study on flutter characteristics of airfoil[J]. .

References

[1] 中国民用航空局. CCAR-25-R4，运输类飞机适航标准[S]. 中国民用航空局, 2011.
[2] 赵忠良,吴军强,李浩,等. 2.4 m跨声速风洞虚拟飞行试验技术研究[J]. 航空学报, 2016(2): 504-512.
[3] 孙亚军,梁技,杨飞,等.超临界机翼跨音速颤振风洞试验研究[J].振动与冲击, 2014(4): 190-194.
[4] LI X L, XU L J, TAN C, et al. Real-Time Measurement of Aerodynamic Deformation of Wing by Laser Range Finder [C]//Instrumentation and Measurement Technology Conference (I2MTC), 2010: 1581-158.
[5] BARROWS, D A. Videogrammetric Model Deformation Measurement TechniqueforWindTunnelApplications(Invited)[C]//AIAA-2007-1163,45th AIAA Aerospace Sciences Meeting and Exhibit, Reno, Nevada,Jan 8-11, 2007.
[6] BA KUNOWICZ J, MEYER R. In-Flight Wing Deformation Measurements on a Glider[C]//RaeS Research Aircraft Opearations Conference.2014: 1-12.
[7] NV NGUYEN,M TYAN, JWLEE, et al. Investigations on stability and control characteristics of a CS-VLA certified aircraft using wind tunnel test data[J]. Proceeding of the Institution of Mechanical Engineers Part G Journal of Aerospace Engineering, 2016, 230(14): 2728-2743.
[8] LIU J M, JIANG X H, QIN Y L, et al. Numerical simulation of bird impact on solid-element hollow blades by using fluid-solid coupling method[J]. Journal of Aerospace Power, 2010, 25(10): 2211-2216.
[9] 宗宁,杨广珺,吕胜利. 大展弦比机翼流固耦合迭代求解模拟.航空计算技术[J]. 2013, 43(3): 13-16.
[10] 朱世权,李海元, 陈志华, 等. 弹性机翼静气动弹性数值研究[J].工程力学, 2017, 34(S): 326-332.
[11] 汪亚真,刘明,王成军, 等. 可变结构小型多旋翼无人飞行器的设计[J]. 机械设计与制造, 2016(4): 186-189.
[12] 仲继泽,徐自力. 基于动网格降阶算法的机翼颤振边界预测[J].振动与冲击, 2017(4): 185-191.
[13] 聂雪媛,黄程德, 杨国伟. 基于CFD/CSD耦合的结构几何非线性静气动弹性数值方法研究[J].振动与冲击, 2016, 35(8): 48-53.
[14] 杨秋明,朱永峰,刘清.基于流-固耦合传热的热气防冰系统干空气飞行蒙皮温度场计算研究[J].空气动力学报,2016,34(6): 721-724.
[15] DING J M, WANG Z G, ZHONG C B. Model and harmonic response analysis of composite resin concrete[J]. Advanced Materials Research,2011, 391-392: 349-353.
[16] 秦可伟,马贵春, 席园, 等. 基于ANSYS 的机翼动力学分析[J]. 航空计算技术, 2014(2): 106-109.
[17] 杨贤文,余立,吕彬彬,等.静气动弹性模型高速风洞试验研究[J].空气动力学学报, 2015, 33(5): 667-672.
[18] LIU T, MONTEFORT J, GREGORY J, et al. Wing Deformation Measurements from Pressure Sensitive Paint Images Using Videogrammetry[C]//AIAA Fluid Dynamics Conference and Exhibit, 2011:343-349.